EP1876327A2 - Joint d'étanchéité pour moteur à turbine - Google Patents
Joint d'étanchéité pour moteur à turbine Download PDFInfo
- Publication number
- EP1876327A2 EP1876327A2 EP07252689A EP07252689A EP1876327A2 EP 1876327 A2 EP1876327 A2 EP 1876327A2 EP 07252689 A EP07252689 A EP 07252689A EP 07252689 A EP07252689 A EP 07252689A EP 1876327 A2 EP1876327 A2 EP 1876327A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- seal
- thermal expansion
- land
- expansion member
- support structure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/502—Thermal properties
- F05D2300/5021—Expansivity
- F05D2300/50212—Expansivity dissimilar
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S277/00—Seal for a joint or juncture
- Y10S277/931—Seal including temperature responsive feature
Definitions
- This invention relates to an air seal that is suitable for use in, for example, a turbine engine.
- seals are used to prevent undesired fluid flow within, for example, a turbine engine. These seals are used to seal static and rotating structures within the engine. Typical types of seals include air seals, labyrinth seals, brush seals, knife-edge seals and honeycomb seals.
- a typical seal arrangement within a turbine engine has the seal hard mounted or affixed to a support structure. As thermal growth of various components occurs within the turbine engine, the seal moves away from the seal land causing the seal to seal land gap to grow increasing fluid leakage across the seal. What is needed is a seal that remains in close proximity to the seal land during thermal growth of the turbine engine.
- a preferred turbine engine disclosed herein includes a first turbine structure that supports a seal.
- the seal is movable within a recess of the first turbine structure.
- the seal is arranged in close proximity to a seal land of a second turbine structure for preventing a fluid from leaking past the seal and seal land.
- a thermal expansion member interconnects the first turbine structure and the seal.
- the thermal expansion member expands in response to an increase in temperature to move the seal toward the seal land preventing the typical enlarged gap between the seal and seal land resulting from thermal growth.
- the thermal expansion member which is arranged at each opposing end of a seal segment, is a bimetallic coil spring supported on the first turbine structure by a cage. A free end of the coil spring is secured to the seal at the opposing end portions.
- a seal is provided that remains in close proximity to the seal land during thermal growth of the turbine engine.
- a turbine engine 10 is schematically shown in Figure 1.
- the turbine engine 10 includes a seal arrangement 11 having a support structure 12 such as a housing 13 (shown in Figure 2).
- the seal 14 can include two or more segments 15a, 15b that create a seal about a seal land 16 such as a surface of a shaft.
- a seal land 16 such as a surface of a shaft.
- any number of segments can be used. The uniformity of clearance improves when more segments are employed.
- the seal 14 can be linear or annular in shape.
- the seal land 16 can be provided by any static or rotating structure.
- the seal 14 can be of any suitable type such as an air seal, labyrinth seal, brush seal, knife-edge seal or honeycomb seal.
- a thermal expansion member 18 is schematically shown interconnecting the seal 14 to the support structure 12.
- the seal 14 is permitted to float relative to the support structure 12.
- a gap 20 is arranged between the seal 14 and support structure 12 to permit the seal 14 to move toward and away from the seal land 16.
- One example seal arrangement 11 is shown schematically in more detail in Figure 3.
- the segment 15a of the seal 14 provides opposing end portions 22.
- the thermal expansion member 18 is arranged at each of the opposing end portions 22 to provide adequate support for the segment 15a.
- the support structure 12 includes a recess 36 that receives and locates the seal 14.
- the gap 20 provides a distance D between the seal 14 and support structure 12.
- the thermal expansion member 18 is constructed from a bimetallic material, as is well known in art.
- the bimetallic material is arranged in a coil spring configuration and supported by a cage 24 using a pin 30.
- the cage 24 ensures that the coils 38 move in a desired direction.
- the cage 24 is secured to the support structure by a threaded fastener 26, in the example shown.
- the cage 24 is secured to the seal 14.
- the bimetallic material 28 is arranged in coils 38 and includes a free end 32 that is secured to the seal 14 using a fastener 34 such as a rivet. As the temperature increases, the coils 38 lengthen to move the seal 14 away from the support structure 12 and toward the seal land 16 to ensure that the seal 14 is in close proximity to the seal land 16 in a region R.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/481,453 US7572099B2 (en) | 2006-07-06 | 2006-07-06 | Seal for turbine engine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1876327A2 true EP1876327A2 (fr) | 2008-01-09 |
EP1876327A3 EP1876327A3 (fr) | 2011-03-09 |
EP1876327B1 EP1876327B1 (fr) | 2012-09-19 |
Family
ID=38330173
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07252689A Expired - Fee Related EP1876327B1 (fr) | 2006-07-06 | 2007-07-04 | Joint d'étanchéité pour moteur à turbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US7572099B2 (fr) |
EP (1) | EP1876327B1 (fr) |
JP (1) | JP2008014298A (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2991404A1 (fr) * | 2012-05-31 | 2013-12-06 | Snecma | Partie fixe d'un dispositif de joint d'etancheite a labyrinthe comportant une piece intermediaire |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8398090B2 (en) | 2010-06-09 | 2013-03-19 | General Electric Company | Spring loaded seal assembly for turbines |
CH704995A1 (de) * | 2011-05-24 | 2012-11-30 | Alstom Technology Ltd | Turbomaschine. |
US10801729B2 (en) | 2015-07-06 | 2020-10-13 | General Electric Company | Thermally coupled CMC combustor liner |
US11149646B2 (en) | 2015-09-02 | 2021-10-19 | General Electric Company | Piston ring assembly for a turbine engine |
US10197278B2 (en) | 2015-09-02 | 2019-02-05 | General Electric Company | Combustor assembly for a turbine engine |
US10168051B2 (en) | 2015-09-02 | 2019-01-01 | General Electric Company | Combustor assembly for a turbine engine |
US9976746B2 (en) | 2015-09-02 | 2018-05-22 | General Electric Company | Combustor assembly for a turbine engine |
US10837640B2 (en) | 2017-03-06 | 2020-11-17 | General Electric Company | Combustion section of a gas turbine engine |
KR20180122913A (ko) * | 2017-05-05 | 2018-11-14 | 이종철 | 개스킷용 실링부재 및 이를 포함하는 개스킷 |
US11402097B2 (en) | 2018-01-03 | 2022-08-02 | General Electric Company | Combustor assembly for a turbine engine |
US20230106380A1 (en) * | 2020-03-30 | 2023-04-06 | General Electric Company | Seal assembly for a rotary machine |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3146992A (en) * | 1962-12-10 | 1964-09-01 | Gen Electric | Turbine shroud support structure |
GB1381277A (en) * | 1971-08-26 | 1975-01-22 | Rolls Royce | Sealing clearance control apparatus for gas turbine engines |
JPS58206806A (ja) * | 1982-05-27 | 1983-12-02 | Toshiba Corp | 蒸気タ−ビンのラビリンスパツキン |
JPS58206807A (ja) * | 1982-05-28 | 1983-12-02 | Hitachi Ltd | 軸流タ−ビンの動翼先端すき間制御装置 |
JPS60111004A (ja) * | 1983-11-21 | 1985-06-17 | Hitachi Ltd | 軸流形流体機械のケ−シング |
EP1215423A2 (fr) * | 2000-12-15 | 2002-06-19 | General Electric Company | Joint brosses à jeu ajustable et méthode d'ajustement |
US20050058540A1 (en) * | 2003-09-12 | 2005-03-17 | Siemens Westinghouse Power Corporation | Turbine engine sealing device |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6929187B2 (en) * | 2000-10-25 | 2005-08-16 | Grundfos Pumps Manufacturing Corporation | Water control fixture having thermostatically controlled bypass valve |
US6840519B2 (en) * | 2001-10-30 | 2005-01-11 | General Electric Company | Actuating mechanism for a turbine and method of retrofitting |
US6969231B2 (en) * | 2002-12-31 | 2005-11-29 | General Electric Company | Rotary machine sealing assembly |
-
2006
- 2006-07-06 US US11/481,453 patent/US7572099B2/en not_active Expired - Fee Related
-
2007
- 2007-04-17 JP JP2007107918A patent/JP2008014298A/ja active Pending
- 2007-07-04 EP EP07252689A patent/EP1876327B1/fr not_active Expired - Fee Related
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3146992A (en) * | 1962-12-10 | 1964-09-01 | Gen Electric | Turbine shroud support structure |
GB1381277A (en) * | 1971-08-26 | 1975-01-22 | Rolls Royce | Sealing clearance control apparatus for gas turbine engines |
JPS58206806A (ja) * | 1982-05-27 | 1983-12-02 | Toshiba Corp | 蒸気タ−ビンのラビリンスパツキン |
JPS58206807A (ja) * | 1982-05-28 | 1983-12-02 | Hitachi Ltd | 軸流タ−ビンの動翼先端すき間制御装置 |
JPS60111004A (ja) * | 1983-11-21 | 1985-06-17 | Hitachi Ltd | 軸流形流体機械のケ−シング |
EP1215423A2 (fr) * | 2000-12-15 | 2002-06-19 | General Electric Company | Joint brosses à jeu ajustable et méthode d'ajustement |
US20050058540A1 (en) * | 2003-09-12 | 2005-03-17 | Siemens Westinghouse Power Corporation | Turbine engine sealing device |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2991404A1 (fr) * | 2012-05-31 | 2013-12-06 | Snecma | Partie fixe d'un dispositif de joint d'etancheite a labyrinthe comportant une piece intermediaire |
Also Published As
Publication number | Publication date |
---|---|
US20080008580A1 (en) | 2008-01-10 |
JP2008014298A (ja) | 2008-01-24 |
EP1876327B1 (fr) | 2012-09-19 |
EP1876327A3 (fr) | 2011-03-09 |
US7572099B2 (en) | 2009-08-11 |
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